Portable object, in particular a watch, provided with a device for detecting the crossing of the karman line, and detection method

Abstract

The watch (2) includes a memory (4) and a detection device (6), the device including an acceleration sensor (8) capable of measuring the acceleration vector of the watch within a three-dimensional coordinate frame (10) linked to the watch, and an electronic unit (12) arranged to process the measurements supplied by the acceleration sensor. The electronic unit (12) is arranged to detect the crossing of the Kármán line by the watch mounted on the rocket, at least for a given type of rocket, solely by the watch mounted on the rocket. The crossing of the Kármán line by the watch is detected by the watch's detection device (6) based on periodic measurements performed by the acceleration sensor from rocket takeoff to the crossing of the Kármán line, as defined prior to space flight, and based on at least one corresponding reference value stored in memory. The Kármán line is defined by a given altitude or a selectable altitude.

Description

Technology Field

[0001] The present invention relates to a portable object, in particular a watch, for astronauts or other individuals traveling through space by rocket or space shuttle. More specifically, the present invention relates to a portable object, in particular a watch, provided with a device for detecting the crossing of Kármán lines, and to a method for detecting the crossing of Kármán lines. Kármán lines define the conventional boundary between Earth's atmosphere and space. While it is generally agreed that this corresponds to an altitude of 100 km, this altitude varies depending on the organization, particularly between 85 km and 110 km. Kármán paths are also boundaries where a spacecraft must fly at a substantial orbital speed to maintain its orbit around Earth in order to sustain flight. Background Technology

[0002] Various watches are worn by astronauts during spaceflight operations. Some watches worn by astronauts were selected for their robustness and precision, lacking features specific to space flight or missions. Other electronic watches, in particular, provide specific functions useful for space missions. These specific functions typically relate to time measurement, for example, for countdowns and / or alarms. means of solving the problem

[0003] The object of the present invention is to provide a portable object, in particular a watch, capable of detecting the crossing of a Kármán line by a rocket or space shuttle (hereinafter collectively referred to as 'rocket') with sufficient accuracy, to at least a given type of rocket (also referred to as a type of launch vehicle in the technical field of spacecraft) carrying the watch.

[0004] In particular, one objective of the present invention is to provide a portable object, particularly a watch, capable of detecting the crossing of Kármán lines autonomously during space flight, particularly without receiving external communication signals and thus without using a global positioning system ('GPS') and without receiving signals related to real-time data of the space flight from the rocket, and is intended to detect the crossing of Kármán lines by the rocket by the portable object mounted on the rocket during space flight.

[0005] Another object of the present invention is to provide a portable object, particularly a clock, capable of detecting the intersection of Kármán lines with satisfactory accuracy by the portable object, which includes a relatively limited but accurate and space-saving technical means that can be easily integrated within the portable object and particularly within the clock.

[0006] The present invention relates to a portable object that can be worn by a user, wherein the portable object comprises a detection device formed by an acceleration sensor capable of measuring the acceleration of the portable object along three orthogonal axes defining a memory, a time base, and a coordinate frame linked to the portable object (i.e., measuring the acceleration vector of the portable object in the three-dimensional coordinate frame of the portable object), and an electronic unit arranged to process the measurements provided by the acceleration sensor. The detection device is arranged, in relation to the memory, to autonomously detect the intersection of a Kármán line by the portable object mounted on the rocket during the space flight of a rocket of a given type, and the Kármán line (L K ) is the given altitude (H D ) or elevation (H) that can be selected by the user directly or through other selectable spatial variables SIt is defined by ). The electronic unit is based on periodic measurements of the acceleration vector of the portable object taken by the acceleration sensor from rocket takeoff until the Kármán line is crossed, and a predetermined reference value stored in memory prior to the takeoff or a predetermined modification factor (F) calculated by the electronic unit and stored in memory prior to the takeoff. C The reference value determined by ) and the Karman line (L before the above takeoff K Altitude (H) selected by the user for ) S It is possible to detect whether the rocket has crossed the Kármán line based on a predetermined reference value and a correction factor (F C ) is the given altitude (H D The electronic unit is arranged to enable the electronic unit to calculate a change in comparison distance over time based on periodic measurements of the acceleration vector of the portable object, so that the electronic unit can detect the crossing of the Kármán line by the portable object and, accordingly, by the rocket, and so that the electronic unit can compare this comparison distance over time with a calculated reference value and a predetermined reference value, respectively.

[0007] Accordingly, it is worth noting that the portable object according to the present invention is designed to autonomously detect the crossing of a Kármán line by the portable object mounted on a rocket of a given type, using only the required technical means, a detection device comprising an acceleration sensor capable of measuring the component of the acceleration vector for the portable object in a coordinate frame linked to the portable object and an electronic unit for processing the measurements supplied by the acceleration sensor, and a memory. Accordingly, the portable object according to the present invention does not require a 3-axis gyroscope, which can certainly be small and formed by a microelectromechanical system (also known as 'MEMS'), but is typically not very accurate and, in some cases, not accurate enough to allow accurate detection of changes in the orientation of the coordinate frame inherent to the acceleration sensor during space flight, in order to determine the vertical component of the rocket's motion acceleration at any time between takeoff and the crossing of the Kármán line and thereby determine its altitude over time. Accordingly, the present invention avoids the problems associated with small gyroscopes, which are relatively inaccurate and therefore cannot provide sufficiently accurate measurements of the angular velocity of a portable object, in order to determine the orientation and position of that moment in space, particularly at that altitude, while a relatively inexpensive accelerometer of the same size and small dimensions can provide accurate acceleration measurements along three axes.

[0008] In a major embodiment, the portable object is a clock.

[0009] In a preferred embodiment, the acceleration sensor is a microelectromechanical system (also referred to by the acronym 'MEMS'). Such a sensor is small and can be easily integrated into a watch. It should be noted that despite its small size, such an acceleration sensor can be very accurate. By selecting such an acceleration sensor, the aforementioned predetermined reference value is also advantageously defined based on the nominal kinetic acceleration for the rocket. The term 'kinetic acceleration' is understood to mean acceleration corresponding to the time derivative of velocity, and this kinetic acceleration defines a vector that is always tangent to the rocket's trajectory, that is, a vector collinear with the vector of the portable object in space, that is, the instantaneous direction vector of the rocket. The term 'nominal' is understood to mean a value given in this specification for the type of rocket or a specific rocket; thus, in the context of the present invention, it is a theoretical value that depends on the predicted time for the rocket, which is derived from its design and from the plan of space flight with such a rocket, in particular from the time from its launch until it crosses the Kármán line. However, it should be noted that MEMS-type accelerometers do not provide motion acceleration, but rather provide appropriate acceleration that does not make it possible to determine motion acceleration—particularly the vertical component of such acceleration, which is primarily considered when determining the instantaneous altitude of the rocket—in the absence of sufficiently precise data regarding the instantaneous orientation of the rocket in space. As will become apparent from the following detailed description, the present invention provides a notable solution to this problem.

[0010] In a preferred alternative embodiment, the detection device is arranged so that the comparison distance is calculated based on the acceleration vectors measured by the acceleration sensor and the norms of those components given in the coordinate frame linked to the portable object, and the electronic unit is arranged so that the unit can calculate these norms. More specifically, the acceleration sensor provides acceleration vectors in an appropriate coordinate frame, but the norm of the acceleration vectors is independent of the coordinate frame, that is, invariant regardless of the spatial orientation of the coordinate frame in which these acceleration vectors are provided, so that the ambiguity of the orientation of the measurement coordinate frame for the acceleration measurements is no longer a problem. This preferred alternative embodiment is highly advantageous because it overcomes the fact that the coordinate frame linked to the portable object—that is, the coordinate frame defined by the acceleration sensor fixed to the portable object—has a variable orientation with respect to the ground coordinate frame during space flight between the rocket launch base and the Kármán line, particularly because the rocket does not follow a vertical linear trajectory. In addition, the orientation of the portable object can change over time relative to the rocket as a result of the movement of the user wearing the portable object.

[0011] According to an embodiment of the advantageous alternative, the modification factor is equal to the above-determined reference value divided by a given degree.

[0012] According to a general embodiment, a predetermined reference value is defined based on at least one theoretical function of a spatial variable associated with the rocket from rocket takeoff to a given altitude relative to the Kármán line.

[0013] In a general alternative embodiment, the portable object is arranged so that the recording of the fact that the Karman line has been exceeded is made in a protected part of its memory, and thus prevents the user of this portable object from writing to the protected part.

[0014] The present invention also relates to a method for detecting the crossing of a Kármán line by a rocket of a given type carrying a portable object according to the present invention, by the portable object, in accordance with appended claim 1. Alternative embodiments are given in the dependent claims of this claim 1. Brief explanation of the drawing

[0015] The present invention will be described in more detail below with reference to the accompanying drawings, which are given as examples by no means limiting. FIG. 1 schematically illustrates a watch according to the present invention, along with various electronic components forming the watch. FIG. 2 illustrates various variables associated with flight along this trajectory and the implementation thereof in a method for detecting the intersection of Kármán lines according to the present invention and in a device for detecting the intersection of Kármán lines according to a major embodiment of the present invention, in addition to the trajectory, and the trajectory taken by the rocket during flight in space between takeoff and the intersection of the Kármán lines is interrupted in the figure. FIG. 3 is an enlarged view of FIG. 2 of the vector sum of various accelerations accompanying the method for detecting the intersection of Kármán lines according to the present invention, and the vertical axis X t and Z t is the rocket trajectory T parallel to and related to the X and Z axes of Fig. 2. F Point P for (x) S They have their origin at (t), and this point P S (t) is the altitude H of the rocket over time. F (t) and horizontal distance E H Defines (t). Figure 4 illustrates the theoretical curve of the acceleration of a specific type of rocket as a function of time. FIG. 5 illustrates a curve showing the inclination angle of the rocket over time, measured during the flight of the rocket, and a theoretical curve for this inclination angle. Figure 6 illustrates a curve providing the theoretical altitude of the rocket over time. FIGS. 7a to 7d illustrate the detection of a Karman line crossing by a clock according to the present invention implementing the detection method according to the present invention and various messages given to a user by a clock according to an alternative embodiment during space flight. FIGS. 8a and 8b illustrate two messages that may be displayed by the watch to the user of the watch according to an alternative embodiment after the watch detects the crossing of the Kármán lines and, more specifically, after the completion of a space flight or mission in a mission. Specific details for implementing the invention

[0016] Embodiments of a portable object according to the present invention are described below with reference to the drawings, wherein the portable object is composed of a clock, and furthermore, a method for detecting the intersection of a Karman line by such a portable object is described according to the main embodiments of the present invention.

[0017] According to a general embodiment, the watch (2) includes a memory (4) and a detection device (6), the device includes an acceleration sensor (8) capable of measuring the acceleration vector of the watch within a three-dimensional coordinate frame (10) linked to the watch (2), and an electronic processing unit (12) (hereinafter also referred to as the ‘electronic unit’) positioned to process the measurements supplied by the acceleration sensor (8). The watch further includes an electronic control unit (14), which is arranged to activate the detection device (6) in response to the operation of an external control member. The watch is equipped with various external control members, in particular two push buttons (16 and 17) and a stem crown (18). The watch may be equipped with a tactile crystal covering a tactile control means, particularly a display means, and such tactile control means is provided, for example, for data input into the watch memory (4) and / or by the display means, to control the display of specific data, particularly before and after a space flight or space mission. In a particular alternative embodiment illustrated in FIG. 7a, the watch includes an analog display (34) formed by watch hands associated with a gradation, and a digital display (30) formed by an electronic display module defining a major part of the dial of the watch (2). It should be noted that the watch hands may typically be used to display time data, as well as to display other things, for example, to display the current stage or event in a detection method, such as the crossing of a Karman line, or to display the correct progress of an operation before a flight or its completion.

[0018] The electronic unit (12), in relation to the acceleration sensor (8) and memory (4), for at least a given type of rocket, is solely by the watch (2) mounted on the rocket, the Kármán line (L) by the rocket. K It is arranged to detect the intersection of the ) lines. Therefore, detection is performed autonomously by the watch during the rocket's space flight via the watch's detection device. Kármán lines (L K ) is the given altitude (H D User-selectable elevation (H) by ) or directly or through the selection of other spatial variables S It is defined by ). The term 'given altitude' is understood to mean an altitude that is predefined / predetermined by an authorized person or company, not by the watch manufacturer or the user. However, in the case of multiple given altitudes, they may be selectable by the user, that is, the user may select a given altitude from multiple given altitudes.

[0019] Kármán line (L) by rocket (22) carrying clock (2) KThe intersection of the karma line can be detected by a detection device (6) based on periodic measurements of the acceleration vector of this clock taken by an acceleration sensor (8) from the takeoff of the rocket to the intersection of the karma line and a reference value corresponding to an altitude defined for this karma line, which is recorded in the memory (4) of the clock prior to space flight, and is intended to be detected by a clock mounted on the rocket during space flight at the intersection of the altitude defined for the karma line. Alternative embodiments for defining and calculating this reference value are given below. The clock includes a time base that allows periods for taking periodic measurements of the acceleration vector to be determined continuously. More generally, in the case of a portable object, this portable object includes a time base arranged to determine continuous periods, thus enabling the detection device to perform periodic measurements of the acceleration vector. In an alternative embodiment, the time base may be a unit separate from and associated with the detection device, particularly to allow periodic activation of the acceleration sensor. In another alternative embodiment, the time base is integrated within the detection device. In a specific alternative embodiment, this time base is directly associated with an acceleration sensor to clock measurements of the acceleration vector.

[0020] More specifically, the reference value is a predetermined reference value already stored in memory or calculated from an electronic unit and a correction factor (F C It is determined by ) and is a reference value that is predetermined in memory (4) and previously stored, and altitude (H S ) is a Kármán line (L) by the user K It is selected for ). The predetermined reference value and correction factor are for a given altitude (H DIt is relative to ). The electronic unit (12) is arranged so that the electronic unit can calculate a change in comparison distance over time based on periodic measurements of the rocket's acceleration, and so that the electronic unit can compare this comparison distance over time with a calculated reference value and a predetermined reference value, respectively, so that the electronic unit can detect the crossing of the Kármán line by the clock (2) and, accordingly, by the rocket (22). The reference value is advantageously recorded in memory (4) by a specific device configured to supply this reference value to the clock when the clock is programmed 'at the factory' or subsequently. In a simpler alternative embodiment, the clock may be arranged so that the reference value is input into the clock, i.e., its memory (4), through a control member equipped with the clock.

[0021] According to an embodiment of a favorable alternative, the modification factor (F C ) is the above-determined reference value at the given altitude (H D It is the same as dividing by ).

[0022] According to an embodiment of a preferred alternative, a predetermined reference value is the Kármán line (L) from the rocket launch. K Given altitude (H) for ) D It is defined based on at least one theoretical function of the spatial variable associated with the above rocket.

[0023] In a first specific embodiment, the memory (4) has a plurality of given heights (H Dj It is arranged to include a plurality of predetermined reference values, each corresponding to j = 1 to J). Each of the predetermined reference values ​​is generally defined based on at least one theoretical function of a spatial variable relating to the rocket, from rocket takeoff to a corresponding given altitude, and the given altitudes (H DjEach of the above can be selected by the user so that the comparison distance over time, calculated when the clock detects the intersection of the Karman lines, is compared with a corresponding predetermined reference value.

[0024] In a second specific embodiment, the memory (4) has a plurality of given heights (H Dj Multiple modification factors (F) each associated with , j = 1 to J) Cj It is arranged to include ( , j = 1 to J). Modification factors (F Cj Each of ) is automatically detected by a detection device or optionally by the user, Karman line (L K Altitude selected by this user for ) (H S It can be selected as a function of ), wherein the comparison distance according to the calculated time when the clock detects the intersection of the Kármán lines is selected as a selected modification factor and a selected altitude (H S It allows comparison with the reference value determined by ).

[0025] In an advantageous alternative embodiment of the second specific embodiment, a plurality of predetermined reference values ​​are a plurality of given altitudes (H Dj Each is defined for ), and each of the predetermined reference values ​​is defined in a general manner based on at least one theoretical function of a spatial variable relating to the relevant rocket from rocket takeoff to a given altitude corresponding to rocket takeoff. Multiple modification factors (F Cj ) are each multiple given altitudes (H Dj It is identical to multiple predetermined reference values, each divided by ). Each modification factor is selectable for the Kármán line and accordingly variable altitude (H SBy obtaining a reference value through multiplication with ), it is possible to make comparison with the comparison distance supplied by the detection device during the space flight of the related rocket in the electronic unit of the clock possible, and thereby enable the crossing of the Kármán line to be detected by the clock and, accordingly, by the rocket.

[0026] According to a preferred embodiment, the acceleration sensor (8) is formed by a MEMS (microelectromechanical system).

[0027] According to a preferred embodiment, in an event where only one predetermined reference value is provided, this predetermined reference value is also defined based on the nominal motion acceleration of the rocket. Additionally, in an event where multiple reference values ​​are provided, each predetermined reference value is based on a given altitude (H) relative to the Kármán line from the rocket takeoff. D It is defined based on the nominal motion acceleration of the rocket up to ).

[0028] Hereinafter, a method for detecting a Kármán line crossing by a rocket using a clock according to the present invention is described. The following description makes it easier to explain how various variables and functions are defined and / or obtained and how they are involved in the context of the present invention. This detection method can be implemented by a clock according to the principal embodiment described below.

[0029] The present invention relates to a given type of rocket (22) and, during the space flight of this rocket, at a given altitude (H D by ) or selected altitude (H S The Kármán line (L) defined by ) KThe invention relates to a detection method for detecting the intersection of ) and the detection is formed by a portable object that can be worn by a user, particularly mounted on this rocket, by a memory (4), a time base, and an acceleration sensor (8), and in a three-dimensional coordinate frame (10) linked to this watch, the appropriate acceleration vector (a) of the watch. M * This is performed by a watch (2) including a detection device (6) arranged to measure ), and by an electronic unit (12) arranged to process measurements supplied by an acceleration sensor, and an appropriate acceleration vector (a M * ) is the motion acceleration vector (a) of this clock at any moment / any time (t) in the first approximation for the rocket. * gravitational acceleration vector (a) at ) E * It is the same as removing ) . This text contains an asterisk ( * It should be noted that while ) is used to represent a vector, in Figures 2 and 3, the vector is indicated in the conventional way by an arrow positioned over the relevant variable. In general, the appropriate acceleration vector of a clock is equal to the vector sum of the forces experienced by the clock, excluding gravity, divided by the mass. In other words, the appropriate acceleration of an object is the acceleration that this object experiences with respect to an observer in free fall.

[0030] The detection method includes a preliminary phase on a portable object mounted on a rocket for planned space flight, and the preliminary phase includes the following preliminary steps:

[0031] A) From the rocket takeoff defining time zero, at least the Kármán line (L K Given altitude (H) for ) D As a function of time (t) until the intersection of ), the nominal motion acceleration (A) for the rocket (22) N(t)) step, which provides a nominal motion acceleration that is a scalar value in units equivalent to the Earth's gravitational pull (the norm of the nominal motion acceleration vector) (this dimensionless scalar value thus corresponds to the norm of the nominal motion acceleration vector divided by the norm of the Earth's gravitational pull, see FIG. 4).

[0032] B) Altitude given from rocket takeoff (H D The theoretical angle of inclination (θ) for a given type of rocket, with respect to the horizontal plane and as a function of time (t), up to at least one intersection of ). Τ Step of providing (t)) (see Fig. 5).

[0033] C) Altitude given from rocket takeoff (H D Theoretical flight time (T) for a given type of rocket up to the intersection of ) K The step of providing or determining ).

[0034] D) Based on the above nominal motion acceleration and the above theoretical inclination angle, the theoretical appropriate acceleration as a function of time for a given type of rocket (A PT Determining (t), the value of this theoretical appropriate acceleration is defined by the following equation in units equivalent to the Earth's gravitational pull:

[0035]

[0036] E) By numerical and / or mathematical means, time zero (t = 0) corresponding to rocket takeoff and time (T) corresponding to the theoretical flight time K Between ), the theoretical optimal acceleration (A PT The theoretical measured distance (D) defined by the double integral of (t) or by the double integral of the theoretical appropriate acceleration less than the norm of gravitational acceleration. MT Step of calculating ); theoretical measured distance (D MT ) the Kármán line (L K Given altitude (H) for ) DDivided by ) is the modification factor (F) for a given type of rocket C Defines ).

[0037] F) Theoretical measurement distance (D MT ) and / or modification factor(F C The step of recording ) into the clock memory, and thereafter, this modification factor (F C ) is the reference distance (D) where applicable. MR In order to obtain ), prior to rocket takeoff defining the start of the space flight, a selected altitude (H S It is multiplied by ).

[0038] G) A step of activating the detection device of the clock mounted on the rocket before the rocket takes off.

[0039] Subsequently, the detection method includes a detection phase comprising the following detection steps:

[0040] H) The appropriate acceleration vector of the clock in the 3D coordinate frame of this clock is measured by the detection device at the frequency (F M Periodically measured in ), and in the electronic unit, for each measurement, the norm (A) of the measured appropriate acceleration vector M (t n The step of calculating each of )) and the modified norm is the norm less than the norm of gravitational acceleration (A M (t n Equivalent to )) and t n is the same time as n·P, n is the number of measurements performed at least since rocket takeoff, incrementing by 1 unit with each new measurement, and P is the time period defined by the measurement frequency.

[0041] I) In an electronic unit, a step of numerically calculating the double integral over time of the norm of the appropriate acceleration vector of the clock from rocket takeoff, at least from each rocket takeoff, wherein each of these norms is less than the norm of gravitational acceleration, and the norm of the appropriate acceleration vector is at times (t mComparison distance (D) for ) C (t m The above values ​​(A) of the appropriate acceleration vectors measured periodically to obtain )) M (t n It is determined based on )), where m is a positive integer, and each m corresponds to one of the above numbers n.

[0042] J) Each comparison distance (D C (t m )), given altitude (H D In the case of ), the theoretical measured distance (D MT Compare with ) or the selected altitude (H S In the case of ), the reference distance (D MR Compare with ), and the comparison distance (D C (t m )) is the theoretical measured distance (D MT ) or reference distance (D MR A step of recording the detection of the intersection of the Karman line by the detection device and by the portable object in the memory of the portable object when each is greater than ).

[0043] In an embodiment of a preferred alternative to the detection method, the acceleration sensor used to measure the appropriate acceleration vector of the clock, and thereby typically the rocket, is a microelectromechanical system (MEMS) integrated into the clock.

[0044] With respect to Step A), FIG. 4 shows the altitude (H) given from rocket takeoff for a specific rocket. D Nominal motion acceleration (A) beyond the Kármán line defined by ) N Illuminate an example of the curve of (t). Acceleration (A N Supplying (t)) this acceleration (A) during multiple consecutive times, especially periodic times, from takeoff until crossing at least a given altitude. NIt should be noted that this can be accomplished by supplying at least a plurality of predefined values ​​of (t). In addition, as can be seen in the graph of FIG. 4, the theoretical acceleration of motion (A N (t) can instantaneously become a negative value, meaning the rocket's velocity can instantaneously decrease. Therefore, the nominal kinetic acceleration is provided with its mathematical sign, and this sign must be entered into the formula given in step D).

[0045] In an alternative embodiment, acceleration (A N (t)) is at least a given altitude (H) from takeoff. D The theoretical distance (L) traveled by the rocket over time during at least multiple consecutive times, particularly periodic times, until crossing ) FT It is provided by supplying (t). After that, acceleration (A N (t)) is the theoretical distance traveled by the rocket as a function of time (L FT It is determined mathematically and / or numerically through the double derivative of this theoretical distance from (t). In other alternative embodiments, acceleration (A N (t)) is the theoretical altitude of the rocket over time (H) for at least a plurality of consecutive times, especially in periodic times. FT (t)) and the theoretical trajectory of the rocket in space z = T from its starting point until it crosses at least a given altitude FT It is provided by supplying (x) (for simplicity, in the vertical plane XZ, z is a variable corresponding to altitude, and x is a variable corresponding to the horizontal distance from the rocket's launch point). Then, the nominal motion acceleration (A N (t)) is the theoretical altitude of the rocket (H FT (t)) and the theoretical trajectory (T) followed by this rocket in space FT It is determined mathematically and / or numerically from (x), and these two functions are the theoretical distance (L mentioned above).FT It makes it possible to obtain (t)).

[0046] With respect to step B) of the detection method, FIG. 5 shows the theoretical inclination angle (θ) of the relevant rocket. Τ This is an example of the curve of (t) as a function of time. Fig. 5 shows the curve of the slope angle (θ) measured over time during the space flight of a specific type of rocket. Μ (t)) is additionally plotted. This is the time (T) when the rocket begins to tilt. B This shows that the linear approximation is relatively accurate here from ). time (T B Until ), the rocket is at time zero and time (T B The theoretical slope angle (θ) between ) Τ Follow the vertical direction so that (t)) becomes 90°. Theoretical slope angle (θ Τ Supplying (t)) is this theoretical gradient angle (θ) during multiple consecutive times, particularly periodic times, from rocket takeoff until crossing at least a given altitude. Τ It should be noted that this can be accomplished by supplying at least a number of predefined values ​​of (t).

[0047] FIG. 2 shows the trajectory z = T of the rocket (22). F An example of (x) is shown (this trajectory is interrupted in this figure for reasons of scale). It should be noted that the examples given in the figures do not limit theoretical curves that can be expected in any way, and that these are typically specific to each type of rocket (particularly the type of launch vehicle for the space shuttle). The angle of inclination (θ(t)) at time (t) between the rocket's direction at time (t) and the horizontal plane is its spatial position (P S Rocket trajectory z = T at (t) F It is defined by the tangent line at (x), and the variable (x) is a function of time. Therefore, the tangent function of the angle (θ(t)) is the space position (P of the rocket).S Locus (T) for horizontal distance (x) for (t) F It is identical to the derivative of (x). This is the mathematical relationship tanθ(t) = dT F Provides (x) / dx, where x = E H (t) and E H (t) is the horizontal distance of the rocket from the starting point as a function of time. Similarly, T FT (x) is the theoretical trajectory of a rocket of a given type and θ Τ If (t) is the theoretical inclination angle of this rocket at time (t), then the theoretical inclination angle (θ Τ (t)) is, by mathematical and / or numerical means, the aforementioned mathematical relationship tanθ T (t) = dT FT Theoretical trajectory z = T through (x) / dx FT It can be determined by (x), where x = E HT (t) and E HT (t) is the theoretical horizontal distance of the rocket from the starting point as a function of time. Function E HT (t) is the theoretical locus (T FT (x)) and nominal motion acceleration (A N (t) or the theoretical altitude of the rocket as a function of time (H FT It should be noted that it can be determined mathematically and / or numerically based on (t). Therefore, in an alternative embodiment, the theoretical trajectory of the rocket in space (T FT (x)) and the theoretical horizontal distance of this rocket (E HT By supplying (t)), the theoretical slope angle (θ) in step B) of the detection method Τ (t)) is provided, and this theoretical horizontal distance (E HT (t)) is particularly nominal motion acceleration (A N (t)) and theoretical trajectory z = T FT (x) or alternatively, the theoretical altitude of the rocket (H) as a function of time FTIt can be determined mathematically and / or numerically based on (t).

[0048] Theoretical flight time (T K With respect to step C) concerning ), in a simplified alternative embodiment, it is possible to estimate this theoretical flight time based on at least one previous space flight using a rocket of the relevant type. In an advantageous alternative embodiment that does not require a previous flight, the theoretical flight time (T K ) is the nominal motion acceleration (A N (t)) and the theoretical inclination angle of the rocket (θ Τ It will be determined by mathematical and numerical means based on (t). To this end, the theoretical distance (L) traveled by the rocket as a function of time T By defining (t), the following approach can be taken. The theoretical altitude of a rocket in flight (H FT (t)) and the theoretical distance traveled by this rocket (L T A mathematical relationship can be established between (t). The infinitesimal / elementary variation dH at theoretical altitude FT (t) = dL T (t)·sinθ T (t), where dH FT (t) is the infinitesimal amount of the theoretical displacement divided by the fundamental change. Meanwhile, the change amount dL T (t) = V N (t)·dt, where V N (t) is the nominal velocity of the rocket at time (t), and dt is the infinitesimal / fundamental variation at time. Nominal velocity (V N (t)) is, assuming that velocity is equal to the integral of acceleration with respect to time, the nominal motion acceleration (A N It can be determined mathematically and / or numerically based on (t). Therefore, as a function of given (nominal / theoretical) variables, based on the mathematical relationships given above, we [determine] the theoretical elevation (HFT (t)) infinitesimal / basic change (dH FT (t)) can be defined. This provides the following:

[0049] dH FT (t) = V N (t)·sinθ T (t)·dt, where,

[0050] Theoretical altitude (H FT (t)) is dH calculated by mathematical and / or numerical means FT It is equivalent to the integral with respect to time (t). Theoretical flight time (T K To determine ), Equation H FT (T) = H D As it is released, here H D is the given altitude and T is a variable.

[0051] FIG. 6 shows the nominal motion acceleration (A) given in FIG. 4. N (t)) Curve and the theoretical slope angle (θ) given in Fig. 5 Τ (t) Based on the curve, the theoretical altitude (H) as a function of time FT Illustrates an example of the curve of (t).

[0052] Steps D) and E) of the detection method are theoretical measurement distances (D) corresponding to predetermined reference values. MTIt is characterized by being designed to allow ) to be accurately determined, wherein, in this regard, the comparison distance subsequently and accurately calculated by the electronic unit of the watch can be compared according to a principal embodiment of the present invention based on appropriate acceleration measurements supplied by an acceleration sensor arranged in the watch during space flight by the rocket carrying the watch. In this principal embodiment of the watch, the autonomous detection device is considered to use only an acceleration sensor arranged to measure vectors of appropriate acceleration experienced by the watch as its means of measurement. This method, in advance, that is, in a preliminary stage prior to the space flight, the theoretical measurement distance (D MT The method involves a step of determining the appropriate acceleration of the clock, which is a virtual theoretical distance in that it does not correspond to the distance theoretically traveled by the rocket between the ground and the Kármán line, but corresponds to the theoretical distance resulting from the fact that the appropriate acceleration of the clock is being measured. Additionally, given a limited means of measurement, a reference value will be supplied, which depends only on the norm of the appropriate acceleration—a vector within the coordinate frame of the clock (2) supplied by the acceleration sensor and advantageously modified by the norm of the gravitational acceleration by subtracting the norm of the appropriate acceleration from the norm of the appropriate acceleration—and only on the trajectory of the rocket. Thus, the intersection of the Kármán line is intended to be defined based on the norm of the appropriate acceleration of the clock and the rocket carrying it, which is independent of the spatial orientation of the acceleration sensor coordinate frame as already indicated.

[0053] The detection method considers that the norm of the appropriate acceleration vector for a given kinetic acceleration depends on the tilt of the rocket. In fact, this norm is smaller than the norm of gravitational acceleration and does not provide the kinetic acceleration of the clock / rocket when the rocket does not have a vertical direction. Figures 2 and 3 show the kinetic acceleration (a) for the rocket.* ) and measured appropriate acceleration (a M * ) and gravitational acceleration (a E * Shows the vector relationship between ). Motion vector(a(t) * ) acceleration and measured appropriate acceleration vector (a M (t) * ) is the space position (P) of the rocket at the time of space flight (t). S Corresponding to (t)), and the gravitational acceleration vector (a E * ) is always vertical and independent of the rocket's spatial position. The small centripetal acceleration experienced as the rocket gradually tilts is not considered in the relationship between the rocket's optimal acceleration and its kinetic acceleration, which includes this centripetal acceleration, because this centripetal acceleration is small and negligible for a rocket between the ground and the Kármán line. The detection method is the theoretical optimal acceleration of the rocket (A) as a function of time (t), in the preliminary stage for spaceflight, i.e., in stage D). PT (t)) is the theoretical inclination angle (θ) of the rocket supplied in step A) and step B), respectively. Τ (t)) and nominal motion acceleration (A N It is provided for calculation as a function of (t). Then, in step E), the theoretical measured distance (D MT ) is the time (T) corresponding to the theoretical flight time calculated at time zero (t = 0) and stage C) corresponding to the rocket takeoff. K Theoretical optimal acceleration (A) between ) PT It is calculated by the double integral of (t)), or, advantageously, by the acceleration due to gravity (A E It is calculated by the double integral of these theoretically appropriate accelerations less than the norm of ).

[0054] In the absence of any information indicating that we are speaking of an acceleration vector, it should be noted that this description test refers to the value of the acceleration mentioned (the length of a vector with a mathematical sign given as a function of the direction of motion related only to the acceleration of motion in this description), or the norm of the acceleration vector (i.e., the absolute value of the length of the vector, as in the case of the appropriate acceleration of the rocket and the acceleration of gravity). More specifically, when acceleration is mentioned, it refers to the value of that acceleration, and when the norm of acceleration is mentioned, it refers to the norm of the corresponding acceleration vector, i.e., the absolute value of the acceleration.

[0055] Theoretical measurement distance (D MT ) the Kármán line (L K For a given altitude (H D The division by ) is, in the context of the detection method according to the present invention, for a given type of rocket, a modification factor (F C Defines ).

[0056] Step F) is the theoretical measured distance (D) in the clock's memory before space flight, that is, before rocket takeoff. MT ) and / or modification factor(F C Provides saving ). Modification factor(F C ) is the elevation selected by the user for the Kármán line (H S When it is expected that ) can be provided to the watch, the reference distance (D MR It is useful for obtaining ), and in this case, the modification factor (F C ) is the reference distance (D MR To calculate the selected elevation (H) for the Kármán line S It is multiplied by the given altitude (H D Theoretical measurement distance (D) that is accurately determined for ) MT Given a linear approximation performed from ), this reference distance (D MR It should be noted that ) is actually an approximate theoretical distance.

[0057] Steps H) to J) of the detection method of the present invention relate to the step of detecting the crossing of Kármán lines during the space flight of a rocket of a given type by a portable object according to the present invention, particularly a watch according to the present embodiment. Accordingly, the detection device (6) of the watch (2) has a measurement frequency (F M In ), the components of the clock's appropriate acceleration vector are periodically measured along the three orthogonal axes of the three-dimensional coordinate frame defined by the acceleration sensor, and then the electronic unit, the theoretical appropriate acceleration (A PT (t)) is the theoretical measured distance (D at step E). MT Depending on whether it is reduced by the norm of gravitational acceleration in the calculation of ), each measurement time (t n The norm of these appropriate acceleration vectors measured at ) (A M (t n )), or gravitational acceleration (A E A guy of ) less than a guy (A M (t n Calculate the same modified norm for each measurement as )) and respectively. In order to enable periodic measurements of the clock's acceleration vector, the latter includes a time base arranged to allow for the successive determination of periods corresponding to the planned measurement frequency and thus to enable the detection device to control the acceleration sensor to perform the planned periodic measurements.

[0058] Subsequently, according to the theoretical calculations performed in the previous preliminary stage, the electronic unit (12) [calculates] the appropriate acceleration (A of the clock mounted on the rocket from rocket takeoff over time. P Numerically calculate the double integral of the norm of (t), and favorably, each of these norms is less than the norm of gravitational acceleration. Appropriate acceleration (A P The norm of (t) is generally the time (t m Comparison distance D for ) C (t mThe above norm (A) of the appropriate acceleration vector measured periodically to obtain ) M (t n It is determined based on )) where m is a positive integer, and each m corresponds to one of the above numbers n. In a preferred alternative embodiment, the comparison distance (D C (t n )) is time (t n It is calculated for each measurement occurring at ). Finally, for each comparison distance (D C (t m )) is, preferably in near real-time, a given altitude (H D In the case of ), the theoretical measured distance (D MT Compared to ) or selected altitude (H S In the case of ), the reference distance (D MR It is compared with ) respectively. Comparison distances (D C (t m )) is the theoretical measured distance (D MT ) and reference distance (D MR These are virtual distances such as ). Time (t m During ), comparison distance (D C (t m )) is the theoretical measured distance (D MT Greater than ) or each reference distance (D MR When it is greater than ), the electronic unit of the detection device is the Karman line (L K ) records in the clock's memory the fact that it was crossed by the clock and, accordingly, by the rocket. The rocket's takeoff is measured periodically, and the norm of the appropriate acceleration starting before takeoff (A M (t n It can be easily detected based on )). In fact, as long as this is substantially the same as the gravitational acceleration, the electronic unit can conclude that the rocket has not yet taken off, and, for example, can determine the rocket takeoff time when the measured appropriate acceleration exceeds a predetermined given limit value. The appropriate acceleration of the clock (A P The norm of (t) is the gravitational acceleration (AE In an embodiment of the primary advantageous alternative using a value less than ), considering that this value is theoretically null and practically equal to zero, it should be noted that it is advantageous to start calculating the integral for this appropriate acceleration modified by gravitational attraction before rocket takeoff. Thus, the value of the integral will remain substantially zero before rocket takeoff. It should be noted that the measurements of the appropriate acceleration taken by the acceleration sensor are advantageously filtered to remove any parasitic noise.

[0059] In a specific implementation, the detection method comprises the step of calculating a double integral over time in the electronic unit in step I) as follows: after each measurement of appropriate acceleration, at time t of two consecutive measurements n-1 and t n A constant value (A) for the norm of appropriate acceleration according to each period (P) between C (t n As a step of performing a double integral by increments by defining )), this constant value is the norm(A M (t n )) and / or guy(A M (t n-1 A step of performing a double integral determined by )); then, for each period (P), calculating an increase in velocity corresponding to a constant value (each of said constant values ​​is less than the gravitational acceleration), and then, in the next order, a constant value (A C (t n Based on )) or at this constant value less than the norm of gravitational acceleration and time (t n-1 Estimated velocity (V) at ) E (t n-1 Based on each )) time(t n Estimated velocity (V) at ) E (t n )) and base distance(d n Determine ) and then, time (t nComparison distance (D) for ) C (t n To obtain )) the basic distances (d1 to d) obtained at the end of the previous measurement of appropriate acceleration n-1 The sum of ) base distance(d n It is characterized by being composed of a step of adding ). It should be noted that the calculations provided by the electronic unit advantageously require relatively low computing power.

[0060] The user's Karman limit (L K For the selected altitude (H S In an alternative embodiment provided to allow selection of ), such selection is indirect, that is, the user is provided to select the inclination angle of the rocket provided for the crossing of the Kármán line by this rocket through a control member equipped with a watch. The selection of the inclination angle may consist of entering an arbitrary value based on data regarding the relevant space flight or selecting a specific value from a plurality of proposed values ​​from a list that may be continuously displayed by the watch. This selection is the selected altitude (H S As with the case where ) is supplied directly, it is performed with a given type of rocket and prior to the space flight. Selected altitude (H S ) is determined as a function of the selected slope angle, and the electronic unit (12) is the corresponding selected altitude (H S It is arranged to convert the slope angle supplied by ).

[0061] According to an improved implementation, the detection method according to the present invention has a theoretical measurement distance (D MT ) are multiple distinct given altitudes (H) that can be selected by the user of the watch Dj Determined for each given altitude of , j = 1 to J), and each theoretical measured distance (D MTj ) and / or their respective corresponding modification factors (F Cj) is stored in the clock memory (4) and theoretical measured distances (D MTj One of ) or modification factors (F Cj One of ) is the altitude (H) for the direct or Kármán limit S It is characterized by making it selectable by selecting ). This improved implementation is characterized by the Kaman line (L K For example, regarding altitude (H) between 80 km and 110 km S It should be noted that it is advantageous if an extended range of ) can be selected. In this case, multiple predetermined altitudes include, for example, a value of 85 km for the first part of the range of altitudes selectable between 80 km and 90 km, a value of 95 km for the second part of the range of altitudes selectable between 90 km and 100 km, and a value of 105 km for the third and final part of the range of altitudes selectable between 100 km and 110 km. Thus, multiple theoretical measurement distances (D MTj ) and / or each modification factor (F Cj ) is predetermined and entered into the clock's memory (4). Accordingly, each modification factor is used to provide a specific reference distance for only one part of the range of selectable altitudes based on a theoretical measurement distance for a given altitude that is substantially located in the middle of the relevant part of the range through a linear approach.

[0062] The following is a description of a major embodiment of a clock according to the present invention that enables the implementation of the detection method according to the present invention.

[0063] The clock (2) according to the present embodiment has a detection device (6) that measures the frequency (F MIn ), the components of the appropriate acceleration vector of the clock are arranged so that they can be periodically measured along the three orthogonal axes of the three-dimensional coordinate frame (10) defined by the acceleration sensor (8) and linked to the clock, that is, so that the appropriate acceleration vector can be measured by the detection device in the clock's coordinate frame, and such appropriate acceleration vector is characterized by being equal to the vector sum of the forces of this clock divided by its mass, excluding the force of gravity. It should be noted that such appropriate acceleration vector may be supplied by an acceleration sensor formed by a microelectromechanical system (MEMS) provided in a preferred alternative embodiment. Then, for each measurement, the detection device (6) in the electronic unit (12) receives the norm (A) of the appropriate acceleration vector measured by the acceleration sensor (8). M (t n )) or gravitational acceleration (A E A guy of ) less than a guy (A M (t n It is configured to calculate a modified norm identical to )) and t n is equal to n·P, where n is the number of measurements performed at least after rocket takeoff, incremented by 1 unit for each consecutive measurement, and P is the time period defined by the measurement frequency.

[0064] The electronic unit (12) also has an appropriate acceleration (A P (t)'s, that is, the norm (A) of the appropriate acceleration vector P (t)) of the clock and also of the rocket (assuming that little or no acceleration from the user other than that generated by the rocket on the clock is applied), each is arranged to numerically calculate the double integral over time from at least the rocket takeoff, of such appropriate acceleration / norm less than the norm of gravitational acceleration, and appropriate acceleration (A P (t)) is time (t m Comparison distances (D) for ) C (tm The above norm (A) of appropriate acceleration vectors periodically measured to obtain )) M (t n It is determined based on )), where m is a positive integer and each m corresponds to the number n. Then, the detection device (6) determines each comparison distance (D C (t m )) can be compared with a predetermined reference value stored in memory, or a modification factor (F C Altitude (H) selected through ) S It is configured to be comparable with a calculated reference value obtained for ), and these values ​​and this modification factor were previously defined in the context of a general embodiment of the watch, and thus the comparison distance (D C (t m It can detect whether )) is greater than this predetermined threshold value or whether it is greater than this threshold value.

[0065] According to an embodiment of a favorable alternative, the calculation of the double integral over time performed in the electronic unit (12) is: after each measurement of the appropriate acceleration, at time t n-1 and t n A constant value (A) for the norm of the appropriate acceleration vector according to each period (P) between C (t n By defining )), double integration is performed incrementally, and this constant value is the norm(A M (t n )) and / or guy(A M (t n-1 By performing a double integral determined by )) to calculate, for each period (P), the increase in velocity corresponding to each constant value less than the constant value or the gravitational acceleration, and then in the order of the constant value (A C (t n )) or this constant value and time (t) less than the norm of gravitational acceleration n-1 Estimated velocity (V) at ) E (t n-1Based on each )) at time (t n Estimated velocity (V) at ) E (t n )) and base distance(d n After determining ), time (t n Comparison distance (D) for ) C (t n To obtain )) the basic distances (d1 to d) obtained at the end of the previous measurement of appropriate acceleration n-1 The sum of ) base distance(d n It consists of adding ).

[0066] In a specific alternative embodiment, the watch includes visual and / or vibrating means (vibrator) and / or optionally audible means arranged so that the watch can indicate that it has crossed the Kármán line as soon as the detection device detects that the watch has crossed the Kármán line. The computing power in the watch is time (t n Comparison distance D immediately after each measurement of the appropriate acceleration vector of the clock in ) C (t n If it is sufficient to calculate ), the crossing of the Kármán line by this clock and therefore by the rocket is detected almost in real time.

[0067] In a general alternative embodiment, the clock is arranged to record at least the first crossing of the Karman line by the clock, and preferably each crossing of the Karman line by the clock. Additionally, it includes a display means (30) arranged to automatically and / or at command indicate whether the Karman line is crossed by the clock, and preferably to indicate the number of times this event has occurred.

[0068] According to a preferred alternative embodiment, the watch is arranged to permanently record the detection of the crossing of the Karman line by the watch in memory (4), and this recording is made in a protected part (4a) of memory, so that the user of the watch cannot program this protected part.

[0069] FIGS. 7a through 7d illustrate various messages provided by the watch (2) via the digital display (30) during space flight. By pressing the push button (16) for an extended period, the user aboard the rocket activates the watch mode to detect the crossing of the Kármán line. The watch then displays 'KARMAN DET READY' (Fig. 7a), indicating that the detection device (6) is ready to detect the crossing of the Kármán line by the watch (2) or by the rocket, respectively. The detection device can then determine when the rocket is to take off based on the measurement of the appropriate acceleration of the watch. At this point, the digital display indicates 'KARMAN ON TK OFF' (Fig. 7b), indicating that the detection device is active and the rocket is taking off. The digital display indicates the time elapsed since takeoff, for example, 125 seconds at a given moment, by displaying 'FLIGHT TM 125' (Fig. 7c). Finally, as soon as the clock detects the intersection of the Kármán lines and enters space itself, the clock displays the message 'U ARE IN SPACE' (Fig. 7d, where 'U' is an abbreviation for 'YOU'), that is, it displays that the astronaut has reached space with the rocket.

[0070] FIGS. 8a and 8b provide examples of messages that may be displayed by the watch outside of at least one space mission, in particular, where the watch serves as a mechanism for detecting the crossing of Kármán lines for an astronaut wearing the watch. By pressing two push buttons (16 and 17) simultaneously, the watch displays 'WORN IN SPACE' (Fig. 8a), a message indicating that it has been worn in space and crossed the Kármán lines, based on data stored in a protective portion (4a) formed by its memory, preferably a non-volatile memory ('OTP' memory) that can be written to only once. Preferably, by subsequently pressing the push button (17), the watch displays the 'KARMAN DET NB' message and the number of times the watch has entered space (i.e., 2 in the example given in FIG. 8b).

[0071] It has already been explained that the watch can be arranged to allow input of various selectable parameters and / or variables, particularly the altitude or the intended tilt angle of the rocket relative to the Karman limit at this event. This data can be input specifically through a touchscreen formed on the watch glass and / or through a push button that allows increasing numerical scrolling across part of the digital display (30) and scrolling to stop or be performed at a predicted value. Alternatively, the hands of the analog display (34) can be used for this purpose.

[0072] Theoretical measurement distance (D) defining a predetermined reference value MT A corresponding modification factor (F) that enables the determination of ) and calculated reference values C It should be noted that ) relates to a given rocket type (also referred to as the 'type of launch vehicle') as previously mentioned. In an improved embodiment, the theoretical measurement distance (D MT) and / or corresponding modification factors may be entered into the memory (4) of the watch for various types of rockets. In this case, the watch includes means for selecting the type of rocket for planned detection of the crossing of the Kármán line before space flight. These selection means may use a list providing various types of rockets considered, particularly for detection applications in the watch, which can be viewed by scrolling through the various types of rockets considered by the control member of the watch and by selecting using another control member.

[0073] Finally, each theoretical measurement distance (D MT ) and their respective corresponding modification factors (F C ) is the given altitude (H D It should be noted that this is for ). This given altitude may be an altitude measured from sea level, that is, independently of the rocket launch site, or an altitude measured from a specific launch site.

[0074] In an embodiment of a sophisticated alternative, the launch site can also be selected by the user prior to spaceflight via the watch's control elements and display means. Thus, each launch site corresponds to one or more theoretical measured distances and one or more corresponding correction factors. In this case, the altitude (H selected by the user) S ) will be the altitude of the sea level. Given altitudes (H) used to predetermine one or more reference values D ), and elevations selected by the user (H S For both sides, it is understood that using altitudes measured from any launch location, that is, heights measured from the ground at the rocket's takeoff point, is advantageous because it is simpler.

Claims

Claim 1 Given altitude (H D by ) or selected altitude (H S The Kármán line (L) defined by ) K A method for detecting a crossover by a rocket of a given type during the space flight of the rocket by a portable object worn by a user and carried on board the rocket, wherein the portable object comprises a memory, a time base, and a detection device, wherein the detection device is formed by an accelerometer capable of measuring an appropriate acceleration vector of the portable object in a three-dimensional coordinate frame of the portable object, and by an electronic unit arranged to process measurements supplied by the accelerometer, wherein the appropriate acceleration vector of the portable object is equal to the vector sum of the forces acting on the portable object excluding the force of gravity divided by its mass, and the time base is used to continuously determine a period for measuring the appropriate acceleration vector; the detection method comprises a preliminary preliminary phase for the portable object deployed on board the rocket for the space flight, wherein the preliminary phase comprises the following preliminary steps: - nominal motion acceleration (A) for the rocket of the given type N (t)) is defined as at least the given altitude (H) from the rocket takeoff defining time zero. D A step of providing the nominal motion acceleration as a function of time (t) until the intersection of ), wherein the nominal motion acceleration is a scalar value in units equivalent to the gravitational pull of the Earth; - a given altitude (H) from rocket takeoff D The theoretical angle of inclination (θ) for the rocket of the given type, with respect to the horizontal plane and as a function of time (t), up to at least one intersection of ). Τ (t)) step of providing the given altitude (H) from rocket takeoff; D Theoretical flight time (T) for the rocket of the given type up to the above intersection of ) K A step of determining or providing ) - based on the nominal motion acceleration and the theoretical inclination angle, the theoretical appropriate acceleration (A) as a function of time for the rocket of the given type PT As a step for determining (t), the value of this theoretical optimal acceleration in units equivalent to Earth's gravitational pull is given by the following equation: A step of determining the theoretical appropriate acceleration defined by;- by numerical and / or mathematical means, time zero (t = 0) corresponding to rocket takeoff and time (T) corresponding to the theoretical flight time. K Between ), the above theoretical optimal acceleration (A PT The theoretical measured distance (D) defined by the double integral of (t) or by the double integral of this theoretical appropriate acceleration less than the norm of gravitational acceleration. MT As a step of calculating ), the theoretical measured distance (D MT ) the above Kármán line (L K The above given altitude (H) for ) D Divided by ) is the modification factor (F) for the above-mentioned rocket of the given type. C The theoretical measurement distance (D) defining ) MT Step of calculating ) - The above theoretical measured distance (D MT ) and / or the above modification factor (F C A step of writing ) to the memory of the portable object, wherein this modification factor (F C ) is thereafter, where applicable, the reference distance (D MR In order to obtain ), prior to rocket takeoff defining the start of the space flight, the selected altitude (H) in the electronic unit S A recording step, multiplied by );- comprising a step of activating the detection device of the portable object mounted on the rocket prior to rocket takeoff, and subsequently, the detection method comprises the following detection steps:- measuring the appropriate acceleration vector of the portable object by the detection device at a frequency (F M Periodically measured in ), and in the electronic unit, for each measurement, the norm (A) of this measured appropriate acceleration vector M (t n )) or the above guy (A M (t n In )) the one less than the gravitational acceleration (A M (t n As a step of calculating the one modified by )), t n is the same time as n·P, n is the number of measurements performed at least since rocket liftoff, incrementing by 1 unit with each new measurement, and P is the norm (A) of the measured appropriate acceleration vector, which is the time period defined by the measurement frequency. M (t n A step of calculating )); - In the electronic unit, a step of numerically calculating a double integral over time from at least rocket takeoff, the norm of the appropriate acceleration vector of the portable object or the norm less than the norm of gravitational acceleration, wherein the norm of the appropriate acceleration vector is the time intervals (t m Comparison distance (D) for ) C (t m The above values ​​(A) of the above appropriate acceleration vectors measured periodically to obtain )) M (t n A step of numerically calculating the double integral, determined based on )) where m is a positive integer and each m corresponds to one of the above numbers n; - each comparison distance (D C (t m )), given altitude (H D In the case of ), the above theoretical measured distance (D MT Compare with ) or the selected altitude (H S In the case of ), the above reference distance (D MR Compare with ), and the comparison distance (D C (t m )) is the above theoretical measured distance (D MT ) or the above reference distance (D MR A method for detecting a Karman line intersection by a given type of rocket, comprising a detection phase including the step of recording the detection by the detection device of the intersection of the Karman line by the portable object in the memory of the portable object when each is greater than ). Claim 2 In claim 1, the step of calculating, in the electronic unit, the double integral over time of each of the norms of the appropriate acceleration vector of the portable object or the norm of the gravitational acceleration less than the norm of the appropriate acceleration vector, at time t after each measurement of the appropriate acceleration vector n-1 and t n A constant value (A) for the norm of the appropriate acceleration vector according to each period (P) between C (t n By defining )), double integration is performed incrementally, and this constant value is the norm(A M (t n By )) and guy(A M (t n-1 By performing the double integral determined by )) to calculate, for each period (P), the increase in velocity corresponding to the constant value or the constant value less than the norm of gravitational acceleration, respectively, and then the constant value (A C (t n For each of these constant values ​​less than the norm of gravitational acceleration or )) and time (t n-1 Estimated velocity (V) at ) E (t n-1 Based on )) time(t n Estimated velocity (V) at ) E (t n )) and base distance(d n Determining ), and then, time (t n Comparison distance (D) for ) C (t n To obtain )) the basic distances (d1 to d) obtained at the end of the previous measurement of the above appropriate acceleration vector n-1 The sum of ) base distance(d n A method for detecting the intersection of Kármán lines by a given type of rocket, characterized by being composed of adding ). Claim 3 In claim 1, the theoretical flight time (T K ) is the following formula: Here In the preliminary phase, determined by mathematical and / or numerical solution based on the nominal motion acceleration and the theoretical inclination angle, where H D A method for detecting the crossing of a Kármán line by a given type of rocket, characterized in that the altitude is the given altitude and time (T) is a variable. Claim 4 In claim 1, the selected altitude (H S A method for detecting a Kármán line intersection by a given type of rocket, characterized in that the rocket is selected for the Kármán line intersection by the rocket and is determined as a function of the inclination angle of the rocket supplied to a portable object prior to space flight by the rocket. Claim 5 In claim 1, the theoretical measurement distance is a plurality of distinct given altitudes (H) that can be selected. Dj Determined for each given altitude of , j = 1 to J), and each theoretical measured distance (D MTj ) and / or their respective corresponding modification factors (F Cj ) is stored in the portable object's memory, and the theoretical measured distances (D MTj One of ) or modification factors (F Cj A method for detecting the crossing of a Kármán line by a given type of rocket, characterized in that one of ) can be selected directly or by selecting an altitude relative to the Kármán limit. Claim 6 A method for detecting the crossing of a Karman line by a given type of rocket, characterized in that, in any one of claims 1 to 5, the acceleration sensor is formed by a MEMS (microelectromechanical system). Claim 7 A portable object (2) that can be worn by a user, comprising a memory (4), a time base and a detection device (6), wherein the detection device is formed by an acceleration sensor (8) capable of measuring the acceleration vector of the portable object in a three-dimensional coordinate frame (10) linked to the portable object, and by an electronic unit (12) arranged to process the measurements supplied by the acceleration sensor, and the time base is used to continuously determine a period for measuring an appropriate acceleration vector; and the detection device (6) is formed by the Kármán line (L) by the portable object mounted on the rocket during the space flight of a given type of rocket. K It is arranged to autonomously detect the intersection of ), and the Karman line (L K ) is the given altitude (H D ) or elevation (H) that can be selected by the user directly or by selecting other spatial variables S Defined by ); the intersection of the Kármán line by the above portable object is the Kármán line (L) from rocket takeoff. K Based on periodic measurements of the acceleration vector of the portable object performed by the acceleration sensor up to the intersection of ), and a predetermined reference value stored in the memory (4) prior to takeoff, or a predetermined modification factor (F) stored in the memory prior to takeoff. C ) and the altitude (H) selected by the user relative to the Karman line prior to the above takeoff S Based on a reference value calculated by the electronic unit (12) based on ), it can be detected by the electronic unit (12), and the predetermined reference value and the modification factor (F C ) is the above-mentioned given altitude (H D A portable object (2) characterized in that the electronic unit is configured such that the electronic unit can calculate a change in comparison distance over time based on periodic measurements of the acceleration vector of the portable object and compare this comparison distance over time with a predetermined reference value and each of the calculated reference values, so as to enable the electronic unit to detect the intersection of the Karman line by the portable object. Claim 8 A portable object (2) characterized in that, in claim 7, the detection device (6) is arranged so that the comparison distance is calculated based on the norm of acceleration vectors measured by the acceleration sensor (8) in the three-dimensional coordinate frame (10), and the electronic unit (12) is arranged so that these norms can be calculated. Claim 9 In claim 7, the modification factor (F C ) is the above-determined reference value at the given altitude (H D Portable object (2) characterized by being identical to that divided by ). Claim 10 In claim 7, the predetermined reference value is the Karman line (L) from rocket takeoff. K The above given altitude (H) for ) D A portable object (2) characterized by being defined based on at least one theoretical function of a spatial variable related to the above rocket. Claim 11 In claim 7, the memory (4) is each of a plurality of given altitudes (H Dj A portable object (2) characterized by including a plurality of predetermined reference values ​​for ( , j = 1 to J), each of the predetermined reference values ​​being defined based on at least one theoretical function of a spatial variable for the rocket from rocket takeoff to a corresponding given altitude, and each of the given altitudes being selectable by a user to allow a comparison over time between the comparison distance calculated when the portable object is detected crossing a Kármán line and the corresponding predetermined reference value. Claim 12 In claim 7, the memory (4) is each of a plurality of given altitudes (H Dj It may include a plurality of modification factors for ( , j = 1 to J), each of which allows a comparison over time between the comparison distance calculated when the portable object is detected to cross the Karman line and a reference value determined by the selected modification factor and the selected altitude, such that the Karman line (L K A portable object (2) characterized by being selectable as a high-level function selected by the user for ). Claim 13 In Clause 12, a plurality of predetermined reference values ​​are each a plurality of given altitudes (H Dj A portable object (2) characterized by being defined for ), wherein each of the predetermined reference values ​​is defined based on at least one theoretical function of a spatial variable related to the rocket from rocket takeoff to a corresponding given altitude; and the modification factors are each equal to the predetermined reference values ​​divided by the given altitudes. Claim 14 A portable object (2) characterized in that, in any one of claims 7 to 9 and 11, the acceleration sensor (8) is formed by a MEMS (microelectromechanical system). Claim 15 In claim 10, the acceleration sensor (8) is formed by a MEMS (microelectromechanical system), and the predetermined reference value is also the nominal motion acceleration (A) for the rocket. N A portable object (2) characterized by being defined based on (t)). Claim 16 In claim 12 or 13, the acceleration sensor is formed by a MEMS (microelectromechanical system), and each predetermined reference value is also the nominal motion acceleration (A) for the rocket. N A portable object (2) characterized by being defined based on (t)). Claim 17 In claim 14, the detection device (6) measures the appropriate acceleration vector of the portable object (2) in the three-dimensional coordinate frame (10) by the acceleration sensor (8) at a frequency (F). M It is arranged to measure periodically in ), and this appropriate acceleration vector is equal to the vector sum of the forces acting on the portable object, excluding the force of gravity, divided by its mass, and for each measurement, in the electronic unit (12), the norm (A) of this measured appropriate acceleration vector M (t n )) or the above guy (A M (t n In )) the one less than the gravitational acceleration (A M (t n Calculate the one modified by )) and t n is equal to n·P, where n is the number of measurements performed at least after rocket takeoff, incremented by 1 unit for each consecutive measurement, and P is a time period defined by the measurement frequency; the electronic unit (12) is arranged so that the electronic unit can numerically calculate a double integral over time from at least rocket takeoff to the norm of the appropriate acceleration vector of the portable object or from the norm of the norm of gravitational acceleration less than the norm of the appropriate acceleration vector, and the norm of the appropriate acceleration vector is the times (t m Comparison distance (D) for ) C (t m The norms (A) of the above appropriate acceleration vectors measured periodically to obtain )) M (t n It is determined based on )) where m is a positive integer, and each m corresponds to one of the above numbers n; and the detection device (6) is determined based on each comparison distance (D C (t m )) with a predetermined reference value stored in memory, or a modification factor (F C Altitude (H) selected through ) S Compare with the reference value obtained for ), and accordingly, the comparison distance (D C (t m A portable object (2) characterized by being arranged to detect whether )) is greater than this predetermined reference value or greater than this reference value. Claim 18 In claim 17, the calculation of the double integral over time performed in the electronic unit is: after each measurement of the appropriate acceleration vector, at time t n-1 and t n A constant value (A) for the norm of the appropriate acceleration vector according to each period (P) between C (t n By defining )), double integration is performed incrementally, and this constant value is the norm(A M (t n By )) and guy(A M (t n-1 Perform the double integral determined by )) to calculate, for each period (P), the increase in velocity corresponding to each constant value less than the constant value or the gravitational acceleration, and then the constant value (A C (t n )) (Each of these constant values ​​is less than the norm of gravitational acceleration) and time (t n-1 Estimated velocity (V) at ) E (t n-1 Based on )) time(t n Estimated velocity (V) at ) E (t n )) and base distance(d n Determine ), and then, time (t n Comparison distance (D) for ) C (t n To obtain )) the basic distances (d1 to d) obtained at the end of the previous measurement of the above appropriate acceleration vector n-1 The sum of ) is the basic distance (d n A portable object (2) characterized by being composed of adding to ). Claim 19 A portable object (2) characterized in that, in any one of claims 7 to 13, the portable object comprises visual and / or vibration means and / or audible means arranged to indicate that the portable object has crossed a Karman line as soon as the detection device detects that the portable object has crossed a Karman line. Claim 20 A portable object (2) characterized in that, in any one of claims 7 to 13, the portable object is arranged to record at least a first intersection of a Karman line by the portable object; and the portable object includes a display means (34) arranged to indicate whether the Karman line has been crossed by the portable object, either automatically or at command. Claim 21 In claim 20, the portable object is arranged so as to permanently record the detection of the intersection of the Karman lines by the portable object, or each detection, in the memory, and the recording is performed in a protected part (4a) of the memory, so as not to allow the user of the portable object to program the protected part, characterized in that the portable object (2). Claim 22 A portable object (2) characterized in that, in any one of claims 7 to 13, the portable object is a watch or a wristwatch. Claim 23 In claim 20, the portable object (2) is characterized by being arranged to record each intersection of the Karman lines by the portable object. Claim 24 In claim 23, the portable object (2) is characterized in that the display means (34) is arranged to automatically or at command indicate the number of times the Karman line has been crossed by the portable object.

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