Automatic parachute deployment system, model rocket

Abstract

The application relates to a parachute automatic triggering system and a model rocket. The parachute automatic triggering system comprises a release assembly and a plurality of wind sensing assemblies. The wind sensing assemblies are connected in parallel and electrically connected with the release assembly, so that the wind sensing assemblies are triggered when the wind direction near the wind sensing assemblies changes, and an opening parachute signal is sent to the release assembly. Meanwhile, the parachute automatic triggering system can be applied to the model rocket. When the model rocket reaches the highest point, the posture changes, the acting wind force changes, the wind sensing assembly is turned on, the parachute release signal is automatically triggered, and the parachute is opened. The model rocket can be recovered at the highest point, and the reliability and convenience are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of model rocket, in particular to a parachute automatic triggering system and a model rocket. BACKGROUND

[0002] The parachute system of the model rocket is a commonly used accessory in the model rocket, which is used to recycle the launched model rocket and eliminate the potential danger to the ground personnel and facilities, thus having both economic and safety guarantee.

[0003] In the current market, the release mode of the model rocket is to release the parachute by a combination of a rotating timer and a rubber band. The rotating timer rotates a certain angle to cooperate with the rubber band to release the parachute at a certain time after launching, usually 2-4 seconds. This requires the operator to estimate and determine the highest point of the model rocket flight. Since the water quantity and air pressure added to the model rocket differ in each test, the operator can only make a rough estimate according to the information, and the release time is usually inaccurate, and the timer may not be able to accurately set to the desired time. Therefore, this method makes it difficult to ensure that the parachute opens at the highest point. SUMMARY

[0004] Therefore, it is necessary to provide a parachute automatic triggering system to automatically trigger the parachute opening system of the model rocket at the highest point to realize the recovery of the model rocket at the highest point.

[0005] A parachute automatic triggering system includes a release assembly and a plurality of wind sensing assemblies. The wind sensing assemblies are connected in parallel and electrically connected to the release assembly to trigger the wind sensing assemblies when the wind direction changes and send an opening signal to the release assembly.

[0006] In one embodiment, the release assembly includes a suction piece, a spring, and an electromagnet. The spring is sleeved on the electromagnet, and the spring has a pre-tightening state and a natural state. When the spring is in the pre-tightening state, the electromagnet is connected to the suction piece. When the spring is in the natural state, the electromagnet is separated from the suction piece.

[0007] In one embodiment, the wind sensing assembly includes a wind sensing piece, a connecting piece, a contact piece, a contact head, and a wind sensing base. The first end of the wind sensing piece is connected to the first end of the contact piece through the connecting piece. The second end of the wind sensing piece is a free end and is provided with a soft plastic, which is used to sense the wind direction. The second end of the contact piece is a free end and corresponds to the contact head. The contact head is electrically connected to the release assembly. The connecting piece is hinged to the wind sensing base.

[0008] In one embodiment, the connecting member comprises a first connecting part and a second connecting part; the first connecting part and the second connecting part are sheet-shaped structures with bending angles and are mutually symmetrical; the wind sensing sheet and the contact sheet are clamped between the first connecting part and the second connecting part and are located at the two ends of the bending structure, respectively.

[0009] In one embodiment, the wind sensing assembly is provided in four sets.

[0010] In one embodiment, the attitude assembly is further electrically connected with the release assembly, and the attitude assembly is triggered when the inclination angle exceeds a preset value and sends an opening parachute signal to the release assembly.

[0011] In one embodiment, the attitude assembly comprises an attitude rod base, an attitude rod and an attitude sleeve; the attitude rod base is fixed with a power supply part and a circuit control part; the attitude rod is electrically connected with the release assembly through the circuit control part; the attitude rod base is provided with an attitude rod connecting groove in the center; the attitude rod is in the form of a rod and is gap-fitted in the attitude rod connecting groove at one end and is placed in the attitude sleeve at the other end.

[0012] In one embodiment, the wind sensing assembly is electrically connected with the release assembly through the circuit control part.

[0013] A model rocket applying the automatic parachute triggering system comprises a nose cone, a control cabin and a rocket body connected in sequence from top to bottom; the nose cone is provided with a containing cavity; the parachute is placed in the containing cavity; the release assembly is placed in the containing cavity of the nose cone; the wind sensing assemblies are distributed in the control cabin in a ring shape and are used to sense the wind direction and trigger the wind sensing assemblies when the wind direction changes and send an opening parachute signal to the release assembly.

[0014] In one embodiment, the attitude assembly is provided in the control cabin and is used to sense the inclination angle of the rocket body and trigger the attitude assembly when the inclination angle exceeds a preset value and send an opening parachute signal to the release assembly.

[0015] Compared with the prior art, the automatic parachute triggering system provided by the present application has the following beneficial effects:

[0016] 1. The wind direction near the wind sensing assembly of the control cabin changes due to the attitude change of the model rocket at the highest point, the wind acts on the wind sensing assembly and is thus turned on, and the parachute release signal is automatically triggered to complete the opening of the parachute; the model rocket is recovered at the highest point, and the prior artificial determination is not required, thereby improving the reliability and convenience;

[0017] 2. A set of attitude components are designed in parallel. When the model rocket attitude changes beyond the preset value, the attitude components are triggered and release the parachute signal, complete the parachute opening, avoid the potential danger of personnel and facilities caused by the tilt angle too large due to operation error or sudden crosswind, and ensure the safety of the rocket body.

[0018] 3. The nose cone uses the action of electromagnet and spring to release the parachute, which is reliable and simple, novel structure, and can be reused. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 It is a schematic diagram of the overall structure of the model rocket;

[0020] Figure 2 It is Figure 1 A-A section view;

[0021] Figure 3 It is Figure 2 B, an enlarged schematic diagram of the identified part;

[0022] Figure 4 It is a nose cone structure explosion diagram;

[0023] Figure 5 It is a nose cone change process diagram after the control cabin gives the parachute opening signal

[0024] Figure 6 It is a schematic diagram of the internal structure of the control cabin;

[0025] Figure 7 It is a schematic diagram of the wind sensing component structure;

[0026] Figure 8 It is a schematic diagram of the switch state when the wind direction of the wind sensing component changes;

[0027] Figure 9 It is a schematic diagram of the attitude component conduction;

[0028] Drawing reference: nose cone 1, first nose cone part 11, second nose cone part 12, parachute 13, release assembly 14, suction piece 141, spring 142, electromagnet 143, nose cone bottom cover 15;

[0029] Control cabin 2, power supply component 21, circuit control component 22, attitude component 23, attitude rod base 231, attitude rod 232, attitude sleeve 233, wind sensing component 24, wind sensing piece 241, connecting piece 242, first connecting part 2421, second connecting part 2422, contact piece 243, contact head 244, wind sensing base 245;

[0030] Rocket body 3. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the present application clearer, the present application will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and not to limit the present application.

[0032] It should be noted that all directional indications, such as upper, lower, left, right, front, back, etc. in the embodiments of the present application are only used to explain the relative positional relationship, movement condition, etc. between components in a certain posture (as shown in the drawings), and if the certain posture changes, the directional indications will also change accordingly.

[0033] In addition, the description such as "first", "second" and the like in the present application is only for the purpose of description and cannot be understood as indicating or implying the relative importance of the technical features indicated or implying the number of the technical features indicated. Therefore, the features defined as "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "a plurality of" is at least two, for example, two, three, etc. unless otherwise specifically limited.

[0034] The automatic parachute triggering system provided by the present application realizes automatic parachute opening of the model rocket at the highest point through the wind sensing assembly 24, and further realizes safe rocket body when the attitude of the model rocket in the air changes too much through the attitude assembly 23. The structure is simple, the cost is low, and the automatic parachute triggering system can be applied to various carriers requiring a parachute system, such as solid rocket, water rocket and other model rockets, and is mainly used for water rocket models.

[0035] As shown in FIG. 1, the structure schematic diagram of applying the automatic parachute triggering system provided by the present application to the model rocket is shown, in order to explain the installation and function of the automatic parachute triggering system of the present application. Figures 1-8

[0036] The model rocket comprises a nose cone 1, a control cabin 2 and a rocket body 3 connected in sequence from top to bottom. The nose cone 1 is a conical structure, which has a containing cavity for placing a parachute 13 and a release assembly 14. The lower end of the nose cone 1 is open, and the open end is provided with a nose cone bottom cover 15. The nose cone bottom cover 15 is a cylindrical structure with an outer wall size matching the inner wall size of the nose cone 1. The upper end of the nose cone bottom cover 15 is open, and the lower end is closed with a bottom plate. The bottom plate is provided with a release assembly fixing position.

[0037] When assembled, the nose cone 1 and the nose cone bottom cover 15 are spliced together to form a sealed space. The nose cone bottom cover 15 and the nose cone 1 are connected in a detachable manner, and preferably spliced to facilitate the release of the nose cone 1 when the release assembly 14 is working.

[0038] ​Specifically, the nose cone 1 comprises a first nose cone part 11 and a second nose cone part 12. The first nose cone part 11 is a conical structure, the side surface of which has a notch, and the inside of which is a cavity structure, having a parachute accommodating cavity for placing a parachute 13 and a release assembly accommodating cavity for placing a release assembly 14. The second nose cone part 12 is an arc-shaped sheet structure, the shape of which is adapted to the shape of the side surface notch of the first nose cone part 11.

[0039] The release assembly 14 comprises a suction sheet 141, a spring 142 and an electromagnet 143. The suction sheet 141 is fixed in the release assembly accommodating cavity, the electromagnet 143 is fixed on the release assembly fixing position of the nose cone bottom cover 15 and is opposite to the suction sheet 141, and the spring 142 is sleeved on the electromagnet 143. When the nose cone 1 and the nose cone bottom cover 15 are assembled, the electromagnet 143 and the suction sheet 141 are connected to each other by attraction, the spring 142 is compressed and is in a pre-tightened state, one end of the spring 142 abuts against the suction sheet 141, and the other end of the spring 142 abuts against the nose cone bottom cover 15. When an opening parachute signal is sent in the control cabin 2, the electromagnet 143 loses the attraction to the suction sheet 141, the spring 142 recovers from the pre-tightened state to a natural state, the suction sheet 141 is pushed open, and thus the first nose cone part 11 is pushed out to be released by throwing, the parachute is opened, and the model rocket is recovered. It is worth noting that a certain adhesive tape is arranged on the inside of the first nose cone part 11, the parachute 13 is adhered to the inner wall of the first nose cone part 11 after assembly, the first nose cone part 11 is pushed open by the spring 142 in the throwing process, and thus the parachute 13 is taken out. The suction sheet 141 is made of a metal material that can be attracted by the electromagnet, such as iron, cobalt, nickel, gadolinium and the like, and is preferably made of iron. The suction sheet 141 is fixed in the release assembly accommodating cavity of the nose cone 1 by means of threaded connection, screw connection or buckle connection.

[0040] The control cabin 2 is a cylindrical structure with one open end and one closed end, and a plurality of parallel wind sensing assemblies 24 are arranged in the control cabin 2. The wind sensing assembly 24 is a trigger switch type structure, which is triggered by sensing the wind direction to send an opening parachute signal, so that the release assembly 14 pushes open the nose cone 1 to complete the opening of the parachute.

[0041] Specifically, any one set of wind sensing assembly 24 comprises a wind sensing sheet 241, a connecting piece 242, a contact sheet 243, a contact head 244 and a wind sensing base 245.

[0042] The open end of the control cabin 2 faces the nose cone bottom cover 15, and the closed end side is provided with slot holes corresponding to the number of wind sensing assemblies 24. The width of the slot hole is slightly larger than the width of the wind sensing sheet 241, and the height is appropriate for the wind sensing sheet 241 to move up and down so that the wind sensing assembly 24 can be turned on or turned off.

[0043] The wind-sensing sheet 241 is a long sheet structure with soft plastic at the end, which can sense the direction of the wind.

[0044] The contact sheet 243 is a sheet structure made of metal material with conductive property.

[0045] The connecting piece 242 is composed of the first connecting part 2421 and the first connecting part 2422, which are sheet structures with bending angles and symmetrical to each other. The two ends of the connecting piece 242 are used to clamp the wind-sensing sheet 241 and the contact sheet 243 respectively. One end of the wind-sensing sheet 241 is clamped between the first connecting part 2421 and the first connecting part 2422, and the other end with soft plastic extends from the slot hole of the control cabin 2 and contacts with the air. One end of the contact sheet 243 is clamped between the first connecting part 2421 and the first connecting part 2422, and the other end is a free end corresponding to the contact head 244 and does not contact in the normal state. The contact head 244 is a rectangular body structure made of metal material with conductive property, one of which is set as positive and the other as negative, and is electrically connected with the circuit control component 22.

[0046] The wind-sensing base 245 is fixed at the inner bottom of the control cabin 2 cylinder and near the slot hole of the control cabin 2. Two hinge holes are opened on the wind-sensing base 245. The connecting piece 242 is provided with a hinge rod at the end near the clamped contact sheet 243, which is hinged with the wind-sensing base 245.

[0047] It is worth mentioning that the contact sheet 243 and the contact head 244 are preferably made of copper material. The contact head 244 is not limited to the rectangular body structure shown in the embodiment, but can also be a cylindrical body, a polygonal body structure, etc. The fixing mode of the wind-sensing base 245 can adopt thread connection, screw connection or buckle connection, etc.

[0048] In operation, for example, Figure 8As shown, the model rocket before launch, the wind vane 241 has a soft plastic end in a natural state, the contact 243 and the contact 244 is not in contact, the circuit is broken. When the model rocket is in the ascent phase, the wind speed of the ascent phase acts on the wind vane 241, the end of the soft plastic is pressed down and bent due to the action of the wind force in the ascent phase, the end connected to the wind vane 241 of the connecting piece 242 moves downward, the end connected to the contact 243 moves upward, so that the contact 243 and the contact 244 are not in contact, and the circuit is in an open state. When the model rocket rises to the highest point and begins to descend, the end of the soft plastic of the wind vane 241 senses the wind force in the opposite direction, that is, the end of the soft plastic of the wind vane 241 is lifted upward due to the action of the wind force, the end connected to the wind vane 241 of the connecting piece 242 moves upward, and the end connected to the contact 243 moves downward, so that the contact 243 and the contact 244 are in contact, and the circuit is in a closed state, thereby sending an opening parachute signal to make the release assembly 14 open the nose cone 1 to complete the opening of the parachute.

[0049] It is worth noting that the embodiment preferably provides four sets of parallel wind sensing assemblies 24, and when any one of the wind sensing assemblies 24 senses a change in wind direction, it will trigger the switch to send a signal to open the parachute 13. The four sets of wind sensing assemblies 24 are connected in parallel, and at least one set can sense a change in wind direction, which ensures that the wind force on the leeward surface will not be insufficient due to the reversal of the joint attitude of the rocket body 3, and the wind speed direction change cannot be sensed by the wind sensing assembly 24 due to the change in the attitude of the rocket body.

[0050] Further, the control cabin 2 is also provided with an attitude assembly 23, which includes an attitude rod base 231, an attitude rod 232 and an attitude sleeve 233.

[0051] The attitude rod base 231 is fixedly arranged at the bottom of the closed end of the nose cone bottom cover 15, and is provided with a slot hole for accommodating the power supply component 21 and the circuit control component 22, so as to fix the power supply component 21 and the circuit control component 22. The center position of the attitude rod base 231 is provided with an attitude rod connecting slot.

[0052] The attitude rod 232 is a rod-shaped structure, one end of which is provided with a spherical structure, which is arranged in the attitude rod connecting slot and is in clearance fit with the attitude rod connecting slot, forming a ball head hinged state, and the attitude rod 232 is electrically connected with the release assembly through the circuit control component 22. The other end of the attitude rod 232 is a free end, which is located in the attitude sleeve 233 and rotates around the center of the spherical structure.

[0053] The attitude sleeve 233 is a cylindrical structure open at both ends, with a cap at one end. A mounting hole is located at the center of the closed end of the control cabin 2, extending vertically through the cabin and its inner diameter matching the outer wall size of the attitude sleeve 233. The attitude sleeve 233 is fitted into the mounting hole, with the capped end located inside the control cabin 2 and contacting the inner wall of the closed end of the control cabin 2. It is secured by threaded connection, screw connection, or snap-fit ​​connection. It is worth noting that the attitude sleeve 233 can also be a cylindrical structure open at one end and closed at the other, with a cap at the open end; the remaining connection methods are the same.

[0054] At work, such as Figure 9 As shown, the model rocket flies upwards, with attitude rod 232 located at the center of attitude sleeve 233, and the circuit is open. When the model rocket reaches its highest point, due to the combined effect of the rocket's center and gravity, its attitude will deflect. When the deflection angle exceeds a preset value, the free end of attitude rod 232 contacts the inner wall of attitude sleeve 233, the circuit is turned on, and a parachute opening signal is emitted, causing release assembly 14 to push open nose cone 1 to complete parachute opening. If a sudden strong wind blows the model rocket away during launch, causing it to deflect at an excessive angle, the attitude rod will also be triggered, which also serves a safety protection function.

[0055] The automatic parachute triggering system provided by this invention utilizes the attitude change of the model rocket at its highest point, thereby causing a change in the wind force acting on the wind-sensing component 24, which in turn triggers the parachute trigger signal. The four parallel systems ensure that no single system installed on the back of the rocket body is unable to sense wind changes, or that there is no problem of insufficient sensitivity. Simultaneously, an attitude component 23 is designed in parallel. Since the model rocket typically ascends vertically, its attitude is likely to change at its highest point. The attitude rod 232 and attitude rod base 231 have degrees of freedom of rotation and will rotate under gravity, touching the inner wall of the attitude sleeve 233 below, thus activating the wire trigger switch and releasing the parachute 13. Furthermore, the attitude component 23 also avoids potential dangers to personnel and facilities caused by large-angle tilting of the rocket body due to incorrect operation or sudden crosswinds. The length of the attitude rod 232 and the size of the attitude sleeve 233 are designed to correspond to different maximum lateral flight angles. When a certain value is exceeded, such as 45°, the switch is actively triggered to open the parachute for recovery, improving flight safety.

[0056] The head cone utilizes the electromagnet 143 and spring 142 to reliably and simply release the parachute 13. It has a novel structure and is reusable.

[0057] Any technical features in the above embodiments can be combined, and for the sake of brevity, not all possible combinations are described above, however, any combination of the technical features is deemed to be within the scope of the present disclosure.

[0058] The above embodiments only express several implementation manners of the present application, and the description is relatively specific and detailed, but should not be understood as a limitation on the scope of the application. It should be pointed out that for ordinary skilled persons in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which are all within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the appended claims.

Claims

1. An automatic parachute deployment system, characterized by: The release component and a plurality of wind sensing components are included; The wind sensing components are connected in parallel and electrically connected to the release component, so as to trigger the wind sensing components and send an opening parachute signal to the release component when the wind direction changes at the wind sensing components.

2. The automatic parachute activation system of claim 1, wherein, The release component includes a suction piece, a spring and an electromagnet; The spring is sleeved on the electromagnet, and the spring has a pre-tightening state and a natural state; When the spring is in the pre-tightening state, the electromagnet is connected to the suction piece; When the spring is in the natural state, the electromagnet is separated from the suction piece.

3. The automatic parachute activation system of claim 1, wherein, The wind sensing component includes a wind sensing piece, a connecting piece, a contact piece, a contact head and a wind sensing base; The first end of the wind sensing piece is connected to the first end of the contact piece through the connecting piece, the second end of the wind sensing piece is a free end and is provided with a soft plastic, and the soft plastic is used to sense the wind direction; The second end of the contact piece is a free end and corresponds to the contact head; The contact head is electrically connected to the release component; The connecting piece is hinged to the wind sensing base.

4. The automatic parachute activation system of claim 3, wherein The connecting piece includes a first connecting part and a second connecting part; The first connecting part and the second connecting part are sheet-shaped structures with bending angles and are symmetrical to each other; the wind sensing piece and the contact piece are clamped between the first connecting part and the second connecting part and are located at both ends of the bending structure, respectively.

5. An automatic parachute activation system according to any one of claims 1 to 4, characterised in that, The wind sensing component is provided in four sets.

6. The automatic parachute activation system of claim 5, wherein, The attitude component is also included, which is electrically connected to the release component, is triggered when the inclination angle of the attitude component exceeds a preset value, and sends an opening parachute signal to the release component.

7. The automatic parachute activation system of claim 6, wherein, The attitude component includes an attitude rod base, an attitude rod and an attitude sleeve; The attitude rod base is fixed with a power supply part and a circuit control part, the attitude rod is electrically connected to the release component through the circuit control part, and the attitude rod base is provided with an attitude rod connecting groove in the center; The attitude rod is in the form of a rod, one end of which is placed in the attitude rod connecting groove and is gap-fitted with the attitude rod connecting groove, and the other end is a free end with a rotatable angle and is placed in the attitude sleeve.

8. The automatic parachute activation system of claim 7, wherein, The wind sensing component is electrically connected to the release component through the circuit control part.

9. A model rocket, characterized by, The automatic parachute triggering system of any one of claims 1 to 8 is applied to a model rocket including a nose cone, a control cabin and a rocket body connected in sequence from top to bottom, the nose cone has a containing cavity, and the parachute is placed in the containing cavity; The release component is placed in the containing cavity of the nose cone, and the wind sensing components are distributed in the control cabin in a ring shape and at intervals, so as to sense the wind direction and trigger the wind sensing components and send an opening parachute signal to the release component when the wind direction changes at the wind sensing components.

10. The model rocket of claim 9, wherein, The attitude component is arranged in the control cabin and is used to sense the inclination angle of the rocket body, trigger the attitude component and send an opening parachute signal to the release component when the inclination angle of the rocket body exceeds a preset value.

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